JP3635746B2 - Lubricant supply device for gas turbine engine - Google Patents

Description

[0001]
BACKGROUND OF THE INVENTION
The present invention relates to a lubricant supply device for a gas turbine engine that supplies a lubricant to a gas turbine engine (for example, an aircraft engine) (hereinafter referred to as a lubricant supply device unless otherwise specified).
[0002]
[Prior art]
In general, a gas turbine engine is provided with a lubricant supply device that supplies a lubricant to a rotating portion.
[0003]
[Problems to be solved by the invention]
By the way, in the conventional lubricant supply device, when air is mixed in the lubricant supply passage, the amount of lubricant supplied to the rotating portion decreases, so the supply amount of lubricant is reduced to compensate for the decrease in the amount of lubricant. There is a problem that it is necessary to increase the size and a large pump is required.
[0004]
The present invention has been made in view of the above circumstances, and a lubricant supply device for a gas turbine engine capable of preventing a decrease in the amount of lubricant supplied even when air is mixed into the lubricant supply passage. The purpose is to provide.
[0005]
[Means for Solving the Problems]
The lubricant supply device of the present invention includes a lubricant recirculation passage provided in communication with a lubrication section of a gas turbine engine, and a lubricant pressure feed that is interposed in the lubricant recirculation passage and pumps the lubricant to the gas turbine engine. Means, a lubricant storage means for storing a lubricant to be circulated in the lubricant return path, and a backflow prevention means interposed downstream of the lubricant pressure supply means. And a lubricant recirculation passage downstream of the lubricant pressure feeding means and upstream of the backflow prevention means and an upstream side of the lubricant pressure feeding means. A communication passage is provided, and an orifice portion having a reduced cross-sectional area is formed in the communication passage.
[0006]
[Action]
According to the lubricant supply device of the present invention, even if air is filled between the lubricant pressure feeding means and the backflow prevention means, the communication path is between the upstream side and the downstream side of the lubricant pressure feeding means. Since it is provided so as to communicate with each other, the blocked air is discharged to the downstream side due to the compression of the air by the lubricant pressure feeding means, and the blocked state is eliminated early. Further, since the orifice is provided in the communication path, the amount of lubricant discharged together with air can be minimized, and insufficient supply of lubricant to the engine is prevented.
[0007]
DETAILED DESCRIPTION OF THE INVENTION
Hereinafter, a lubricant supply unit according to an embodiment of the present invention will be described with reference to the drawings.
[0008]
A lubricant recirculation passage 2 is provided in communication with a lubrication portion of a gas turbine engine (aircraft engine) 1, and a lubricant pressure feeding means 3 for pressure-feeding the lubricant to the gas turbine engine 1 is provided in the lubricant recirculation passage 2. The lubricant recirculation passage 2 is interposed in the lubricant recirculation passage 2. The lubricant storage means 4 stores the lubricant to be circulated in the lubricant recirculation passage 2, and the backflow prevention means is provided downstream of the lubricant pumping means 3. (For example, a check valve) 5 is interposed. The lubricant return passage 2 is provided with a lubricant cooling means 6 for cooling the lubricant and a lubricant return means 7 for returning the lubricant.
[0009]
Also, the lubricant recirculation passage 2 downstream of the lubricant pumping means 3 and upstream of the backflow preventing means 5, and the upper part of the lubricant reservoir 4 disposed upstream of the lubricant pumping means 3, Are communicated by the communication passage 10. In the middle of the communication path 10, an orifice portion 11 having a narrow channel cross-sectional area is formed.
[0010]
Next, the operation of the present embodiment will be described.
[0011]
That is, when the gas turbine engine 1 is started or during minus G flight, if air is mixed into the lubricant pressure feeding means 3 from the lubricant storage means 4, the lubricant recirculation between the lubricant pressure feeding means 3 and the backflow prevention means 5 is performed. Air accumulates in the passage 2. Since the backflow prevention means 5 does not open depending on the air pressure, the portion is filled with air and the supply of the lubricant is interrupted.
[0012]
However, in the present embodiment, the downstream side and the upstream side of the lubricant pumping means 3 are communicated with each other by the communication path 10, so that the pressure difference between the downstream side and the upstream side of the lubricant pumping means 3 is filled. The air is discharged to the downstream side, and the interruption of the lubricant supply due to the air filling can be solved.
[0013]
Further, the lubricant is fed to the lubricant storing means 4 side through the communication path 10 by the operation of the lubricant pressure feeding means 3, but the orifice portion 11 is provided in the middle of the communication path 10. The flow rate of the lubricant flowing through the communication path 10 can be made extremely small. Therefore, even if the communication passage 10 is provided, the flow rate of the lubricant that flows through the lubricant recirculation passage 2 and is supplied to the lubricating portion of the gas turbine engine 1 is not significantly reduced.
[0014]
Further, since the structure is such that the downstream side to the upstream side of the lubricant pumping means 3 communicate with each other through the communication passage 10, high reliability can be obtained.
[0015]
Based on FIG. 3 and FIG. 4, a result of a test conducted by attaching the lubricant supply device of the embodiment to an aircraft engine is shown. 3 and 4 show that the supply of the lubricant from the lubricant storing means 4 to the lubricant pressure feeding means 3 is forcibly stopped and the force between the lubricant pressure feeding means 3 and the backflow prevention means 5 is forcibly stopped. The state of supply of the lubricant to the engine 1 when the supply of the lubricant from the lubricant storing means 4 to the lubricant pumping means 3 is restarted after being filled with air is shown. 4 shows a case according to the embodiment of the present invention shown in FIG. 1, and FIG. 3 shows a case where the communication passage 10 and the orifice portion 11 are removed from the one shown in FIG.
[0016]
According to FIG. 3, it can be seen that the supply of the lubricant to the engine 1 is stopped even after the supply of the lubricant from the lubricant storage unit 4 to the lubricant pumping unit 3 is resumed. Further, according to FIG. 4, when the supply of the lubricant from the lubricant storing means 4 to the lubricant pumping means 3 is resumed, the supply of the lubricant to the engine 1 is resumed promptly, as shown in FIG. In addition, it can be seen that it is effective to provide the communication passage 10 and the orifice portion 11.
[0017]
【The invention's effect】
As described above, according to the lubricant supply device for a gas turbine engine of the present invention, the lubricant recirculation passage provided in communication with the lubrication portion of the gas turbine engine, and the lubricant recirculation passage interposed in the lubricant recirculation passage. Lubricant pumping means for pumping the lubricant to the gas turbine engine, lubricant storage means for interposing the lubricant return passage to store the lubricant to be circulated in the lubricant return passage, and the lubricant pumping In the lubricant supply device for a gas turbine engine, comprising a backflow prevention means interposed downstream of the means, a lubricant return passage downstream of the lubricant pressure feeding means and upstream of the backflow prevention means A communication passage that communicates with the upstream side of the lubricant pumping means is provided, and an orifice portion having a narrowed cross-sectional area is formed in this communication passage. For example, lubrication is performed when starting the engine or during minus G flight. Even if the air between the pressure feeding means and the backflow prevention means is filled, this air can be discharged through the communication passage, and thus the lubricant pressure feeding can be stably supplied at the time of engine start or minus G flight. .
[Brief description of the drawings]
FIG. 1 is a diagram illustrating a lubricant supply device according to an embodiment of the present invention.
FIG. 2 is a view showing a lubricant supply device in which a communication path and an orifice portion are removed from what is shown in FIG. 1;
FIG. 3 is a graph showing a test result of the lubricant supply device of FIG. 2;
4 is a graph showing a test result of the lubricant supply device of FIG. 1;
[Explanation of symbols]
1 Gas turbine engine (aircraft engine)
2 Lubricant recirculation passage 3 Lubricant pumping means 4 Lubricant storage means 5 Backflow prevention means 10 Communication path 11 Orifice section

Claims (1)

A lubricant recirculation passage provided in communication with a lubrication portion of the gas turbine engine; a lubricant pumping means interposed in the lubricant recirculation passage for pumping the lubricant to the gas turbine engine; and the lubricant recirculation passage. Lubrication of a gas turbine engine provided with a lubricant storing means for storing a lubricant to be circulated in the lubricant recirculation passage and a backflow prevention means interposed downstream of the lubricant pressure feeding means In the agent supply device, a communication passage is provided which communicates the lubricant return passage on the downstream side of the lubricant pressure feeding means and upstream of the backflow prevention means and the upstream side of the lubricant pressure feeding means. A lubricant supply device for a gas turbine engine, characterized in that an orifice portion for reducing the flow rate of the lubricant flowing through the communication passage in a flow passage cross-sectional area to be smaller than other portions of the communication passage is formed. .

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